CN103375181B - Turbine assembly - Google Patents
Turbine assembly Download PDFInfo
- Publication number
- CN103375181B CN103375181B CN201310158615.2A CN201310158615A CN103375181B CN 103375181 B CN103375181 B CN 103375181B CN 201310158615 A CN201310158615 A CN 201310158615A CN 103375181 B CN103375181 B CN 103375181B
- Authority
- CN
- China
- Prior art keywords
- circumferential slot
- ring element
- attachment part
- ring
- dovetail attachment
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 241000397426 Centroberyx lineatus Species 0.000 claims description 2
- 238000010276 construction Methods 0.000 claims 2
- 238000000034 method Methods 0.000 description 4
- 239000000567 combustion gas Substances 0.000 description 3
- 239000012530 fluid Substances 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 238000013459 approach Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 239000012141 concentrate Substances 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 230000014759 maintenance of location Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000003345 natural gas Substances 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 238000007634 remodeling Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
- F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
- F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/32—Locking, e.g. by final locking blades or keys
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present invention relates to and disclose a kind of turbine assembly, comprise rotor wheel and be formed on the circumferential slot in rotor wheel, circumferential slot comprises even shape of cross section for rotor wheel circumference. This assembly also comprises the first ring member being positioned in circumferential slot, and first ring member is formed at when dovetail attachment part is positioned in circumferential slot and prevents that dovetail attachment part from radially moving, and wherein dovetail attachment part is a part for turbine blade.
Description
Technical field
The present invention relates to turbogenerator, and relate more specifically to turning for turbogeneratorSub-component.
Background technology
Turbine blade or bucket leaf are usually designed to for being arranged on turbine along circumferential direction and turnOn son wheel. Bucket leaf typically uses exterior circumferential dovetail attachment to turbine wheel, exterior circumferentialDovetail comprises the reception dovetail in circumferential recess or the slit on wheel periphery and the leaf that struggles againstThe dovetail of complementation in base portion or root. Upper for these bucket leaves are loaded into wheel, the periphery of wheelOn be cut with part and remove the recess that receives dovetail part, thereby shape in the groove in rotor wheelBecome the opening of general rectangular. Each bucket leaf be then first placed in recess opening andThen around wheel along circumferentially mobile. Opening in circumferential recess causes rotor wheel relatively uniformly to establishDiscontinuity in meter. Therefore, recess opening can become the concentrated source of stress in rotor wheelAnd can cause rotor life to reduce.
Summary of the invention
According to an aspect of the present invention, a kind of turbine assembly comprises rotor wheel and is formed on and turnsCircumferential slot in son wheel, circumferential slot comprises even shape of cross section for the circumference of rotor wheel. ShouldAssembly also comprises the first ring member being positioned in circumferential slot, and first ring member is formed at swallowTail attachment part prevents while being positioned in circumferential slot that dovetail attachment part from radially moving, and wherein dovetail is attachedCompany headquarters is a part for turbine blade.
According to another aspect of the present invention, a kind of turbine assembly comprises: rotor wheel; FormCircumferential slot in rotor wheel, rotor wheel is configured to receive blade; And first ring member andThe second ring element, first ring member and the second ring element are positioned in circumferential slot, first ring memberBe positioned on each side of a part of blade, to be positioned at blade with the second ring elementIn circumferential slot time, prevent that blade from radially moving.
By description taken together with the accompanying drawings below, the advantage of these and other and feature will become moreAdd apparent.
Brief description of the drawings
Be considered to theme of the present invention refers in particular in claims of description ending placeGo out and explicitly call for protection. By detailed description with the accompanying drawing below, of the present invention above-mentionedWith other feature and advantage be apparent, in the accompanying drawings:
Fig. 1 is according to the perspective view of the rotor wheel of embodiment and turbine blade;
Fig. 2 is the perspective view of the turbine blade shown in Fig. 1 and rotor wheel;
Fig. 3 is the cutaway view of the turbine blade shown in Fig. 1 and Fig. 2 and rotor wheel;
Fig. 4 is according to the perspective view of the turbine assembly that comprises locking component of embodiment, this lockDetermine member and be configured to prevent that blade and ring element from moving in rotor wheel; And
Fig. 5 is the perspective view of a part for the turbine assembly shown in Fig. 1.
Embodiments of the invention and advantage are explained with reference to accompanying drawing by the detailed description of exampleAnd feature.
Detailed description of the invention
Fig. 1 is the perspective view of a part for exemplary turbine assembly 100, exemplary turbineAssembly 100 comprises rotor wheel 102, and rotor wheel 102 is configured to receive blade 104. Blade104 comprise dovetail key or attachment part 106, and dovetail key or attachment part 106 are positioned at rotor wheel 102Circumferential slot 108 in. In an embodiment, first ring member 110 and the second ring element 112 quiltsBe placed in circumferential slot 108, and be configured to keep blade 104 and put at blade 104While being placed in circumferential slot 108, prevent that blade 104 from radially moving. In one embodiment, existBlade (comprising blade 104) is installed before, rotor wheel 102 makes first ring member 110 and theTwo ring elements 112 are arranged in circumferential slot 108. Ring element can radially be inserted in groove andSlide axially to match with the wheel side that has formed circumferential slot 108. When being positioned at circumferential slotIn 108 time, first ring member 110 and the second ring element 112 form opening 122, thereby makeObtain and blade and corresponding dovetail attachment part can be inserted in circumferential slot 108. As below retouchedState, after being inserted in opening 122, blade 104 circumferentially slides along circumferential slot 108,To allow, around the circumference of wheel, blade is subsequently installed.
In an embodiment, in the time that blade 104 is arranged in rotor wheel 102, first ring member 110Be positioned at the first side wall 114 of circumferential slot 108 and the first side 116 of dovetail attachment part 106Between. Similarly, in the time that blade 104 is positioned in circumferential slot 108, the second ring element 112Be positioned at the second sidewall 118 of circumferential slot 108 and the second side 120 of dovetail attachment part 106Between. In an embodiment, first ring member 110 and the second ring element 112 respectively with circumferential slot108 the first side wall 114 and the second sidewall 118 are consistent. As shown in the figure, for rotor wheel102 whole circumference, circumferential slot 108 has basic shape of cross section uniformly. Circumferential slot108 shape of cross section can have any suitable shape with receive one or more blades withAnd one or more ring elements. The basic dovetail that the embodiment of illustrated circumferential slot 108 hasShape is greater than dovetail attachment part 106.
In an embodiment, the sidewall in the sidewall on dovetail and rotor wheel 102 can haveDifferent inclined degrees or profile, the profile that wherein ring element sidewall has and the wheel coordinating orThe complementation of dovetail attachment part profile.
The basic shape of cross section uniformly of circumferential slot 108 has reduced in other rotor wheel to be implementedStress concentration point in example in contingent wheel relatively uniformly. Particularly, first ring structureThe opening 122 that part 110 and the second ring element 112 provide and retention performance make the blade canRemain in basic circumferential slot 108 uniformly. In an embodiment, first ring member 110 andTwo ring elements 112 are not attached, fixing or be attached to rotor wheel 102. In other embodiments,One or more rotor wheel that are attached in ring element 110,112. In addition first ring member,110 and second ring element 112 can include the ring element of more formation ring 110 and 112.In one exemplary embodiment, first ring member 110 comprises multiple member parts, for example structurePart part 124. Exemplary loop member can be by 2,3,5,50 until byThe loop section of the determined any suitable quantity of standard of application-specific forms. In another enforcementIn example, each in ring element 110 and 112 is formed by single ring element. In addition root,According to application, shape or the geometric form of the embodiment of first ring member 110 and the second ring element 112Shape can be identical, or can have difformity to meet the blade stowage pattern of expectation. RealExecuting example has reduced the stress relevant to blade stowage groove in rotor wheel and concentrates and be conducive to makeWith alternative lower-cost material, thereby reduce costs.
Dovetail circumferential slot 108 is typically referred to as " circumferentially entering " groove, and reason is blade 104Dovetail attachment part 106 be inserted in groove along circumferential direction substantially. Feature described hereinCan substantially be applied to any airfoil and dish interface. Structure shown in Fig. 1 has only represented and has coveredCover multiple different dish and the blade design of dissimilar turbine.
As used herein, " downstream " and " upstream " is to represent with respect to working fluidFlow through the term of the direction of turbine. So, term " downstream " represent substantially corresponding toThe direction of the flow direction of working fluid, and term " upstream " represents and working fluid substantiallyThe contrary direction of flow direction. Term " radially " the expression fortune vertical with axis or center lineMove or position. May be to have to being described in the parts of different radial positions with respect to axisWith. In this case, if first component is positioned to compare the more close axis of second component,Can state so so herein: first component is with respect to second component " radially inside ".On the other hand, if comparing second component, first component is positioned to further from axis, so hereinIn can state like this: first component is with respect to second component " radially outside " or " locateIn outside ". Term " axially " represents motion or the position parallel with axis. Finally, term" circumferentially " represents motion or the position around axis. Although the emphasis of discussion below mainly existsIn combustion gas turbine, but the theory of discussing is not limited to combustion gas turbine and can appliesIn any suitable plant equipment, establish comprising steam turbine, oil and natural gas machineryStandby and aero-engine. Therefore, discussion herein relates to combustion gas turbine embodiment, butIt is the turbine system that can be applied to other.
Fig. 2 is the perspective view that the turbine assembly 100 from Fig. 1 of multiple blades is installed.Illustrated embodiment shows and receives the rotor wheel 102 of blade 104 and a part for circumferential slot 108,Is the second blade 200, the 3rd blade 202 and quaterfoil 204 after blade 104.In exemplary group process of assembling, first ring member 110 and the second ring element 112 are positioned at circumferentiallyGroove 108 is interior and spaced apart vertically, to receive blade. Therefore, at next number of assembling stepsIn, the first blade 104 is inserted in opening 122 and along circumferential slot 108 and circumferentially slides, withMake it possible to the second blade 200 to be inserted in opening 122. Be inserted at the second blade 200After in circumferential slot 108, the second blade 200 is also along circumferentially sliding, thereby along circumferentially promoting theOne blade 104, is placed into the 3rd blade 202 and dovetail attachment part 206 thereof making it possible toIn opening 122. In an embodiment, repeat basic similarly step with around rotor wheel 102Whole circumference is placed blade.
Fig. 3 is the cutaway view of the turbine assembly 100 shown in Fig. 1 and Fig. 2. Embodiment bagDraw together spaced apart to receive and the first ring member 110 of fixing dovetail attachment part 106 and the verticallyTwo ring elements 112. As shown in the figure, blade 104 comprises airfoil 300, airfoil 300 fromDovetail attachment part 206 extends in the hot gas path of turbine. In multiple embodiment, theOne ring element 110, the second ring element 112 and blade 104 be not by any securing member, stickyKnot agent or other mechanism are attached or be attached to each other. But, during machine operation, bladeDovetail, ring and wheel will form close contact due to centrifugal force. As shown in Figure 5, for exampleThe feature of jut 500 can be formed in each side of circumferential slot 108. Jut 500Prevent the circumferential movement of first ring member 110 and the second ring element 112 and make the blade canBe received in opening 122. Because ring element 110,112 makes the manufacture of circumferential slot 108Tolerance has more flexibilities, and therefore arrangement illustrated has been simplified manufacture process. Particularly, ringMember 110,112 is processed to receive blade 104, simultaneously can be by accuracy lower andTherefore lower-cost process is manufactured circumferential slot 108, for example casting or rolling. In addition, circumferentialGroove 108 and ring element 110,112 can have any suitable geometry with by bladeRemain in groove.
Referring now to Fig. 4, turbine assembly is shown and comprises locking component 400, locking component 400To be placed in the circumferential slot 108 of rotor wheel 102. In an embodiment, locking component 400Be configured to before closed blade is placed in circumferential slot 108, to be placed on circumferential slotIn 108. After inserting closed blade, blade assembly can be along circumferential movement, lockingMember 400 is positioned in the opening 122 between ring element group. Locking component 400 hasShape makes in the time radially moving, and locking component 400 is no longer worked as and placed at gap 108(When dovetail attachment part ring between) in slip. Therefore, the locking component 400 of locking bladeAnd screw 402 prevents that ring element is along circumferentially mobile. In one embodiment, screw 402 clothPut in locking component 400 and be configured to rotating positioning, radially to extend along direction 404Thereby with respect to the position of circumferential slot 108 locked closed blades and ring element 110,112.Screw 402 and locking component 400 can all have screw thread, so that locking component is radially movedMoving. Closed blade is place around rotor wheel 104 circumference during completing assembling process lastBlade. In the illustrated embodiment, blade 406 is to be positioned at blade 410 and locking component 400Between closed blade. Blade 406 and 410 is by first ring member 110 and the second ring element 112Remain in circumferential slot 108, and prevent blade 406 and 410 edges by locking component 400Circumferential direction 408 moves.
Fig. 5 is the detailed perspective view of a part for the turbine assembly 100 shown in Fig. 1. ShouldEmbodiment shows the circumferential slot 108 being formed in rotor wheel 102. Circumferential slot 108 comprises positionJut 500 on each side of groove, wherein in jut 500(jut 500Only have one visible) be formed at first ring member 110 and the second ring element 112 is positionedAfter in groove, prevent that first ring member 110 and the second ring element 112 from moving. Jut 500 is fixedPosition becomes to approach the opening between the smooth corners part 502 and 504 that is configured to receive ring element122. In multiple embodiment, any suitable feature of for example jut, groove and ridge all canFor locating ring member and prevent that ring element from moving with respect to circumferential slot.
Although only the present invention be have been described in detail in conjunction with a limited number of embodiment,Be should be readily appreciated that, the present invention is not limited to this disclosed embodiments. On the contrary, canBy the present invention be modified as be attached to be not described so far but with spirit of the present inventionAny amount of remodeling, modification, the alternative or equivalent arrangements suitable with scope. In addition, althoughEach embodiment of the present invention is described, but should be appreciated that of the present invention eachIndividual aspect can only comprise some in described embodiment. Therefore, the present invention is not lookedFor being subject to the restriction of description above, but only limit by the scope of claimsFixed.
Claims (6)
1. a turbine assembly, described turbine assembly comprises:
Rotor wheel;
Circumferential slot, described circumferential slot is formed in described rotor wheel, and described circumferential slot is for describedThe circumference of rotor wheel comprises even shape of cross section;
More than first ring element, described more than first ring element is positioned in described circumferential slot, instituteAnti-when stating more than first ring element and being formed at dovetail attachment part and being positioned in described circumferential slotStop described dovetail attachment part and radially move, wherein said dovetail attachment part is turbine bladeA part, described more than first ring element defines at least one between described more than first ring elementIndividual opening, described at least one open construction be formed in described dovetail attachment part circumferentially slide into itsBefore fixed position in described circumferential slot, receiving in the radial direction described dovetail attachment part;
More than second ring element, described more than second ring element is positioned in described circumferential slot, instituteStating more than second ring element is formed at described dovetail attachment part and is positioned in described circumferential slotTime prevent that described dovetail attachment part from radially moving, described more than second ring element is described secondBetween multiple ring elements, define at least one opening, described in described at least one open construction is formed inDovetail attachment part circumferentially slides into before its fixed position in described circumferential slot in side radiallyUpwards receive described dovetail attachment part; And
Locking component, described locking component is formed at closed blade and is placed on described circumferentialBefore in groove, be placed in described circumferential slot, wherein said locking component is configured to pass through spiral shellNail radially extends, to lock described closed blade and described more than first with respect to described circumferential slotThe position of at least one in individual ring element.
2. turbine assembly according to claim 1, is characterized in that, described firstMultiple ring elements are positioned at first of the first side wall of described circumferential slot and described dovetail attachment partBetween side.
3. turbine assembly according to claim 2, is characterized in that, described firstMultiple ring elements are consistent with the described the first side wall of described circumferential slot.
4. turbine assembly according to claim 2, is characterized in that, described secondMultiple ring elements are positioned at second of the second sidewall of described circumferential slot and described dovetail attachment partBetween side.
5. turbine assembly according to claim 4, is characterized in that, described secondMultiple ring elements and described more than first ring element are basic identical.
6. turbine assembly according to claim 1, is characterized in that, described circumferentialThe shape of cross section of groove comprises swallowtail shape.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US13/459931 | 2012-04-30 | ||
| US13/459,931 | 2012-04-30 | ||
| US13/459,931 US9068465B2 (en) | 2012-04-30 | 2012-04-30 | Turbine assembly |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103375181A CN103375181A (en) | 2013-10-30 |
| CN103375181B true CN103375181B (en) | 2016-05-04 |
Family
ID=48182757
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310158615.2A Active CN103375181B (en) | 2012-04-30 | 2013-05-02 | Turbine assembly |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US9068465B2 (en) |
| EP (1) | EP2660426B1 (en) |
| JP (1) | JP6106021B2 (en) |
| CN (1) | CN103375181B (en) |
| RU (1) | RU2013119488A (en) |
Families Citing this family (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2014204542A2 (en) * | 2013-04-01 | 2014-12-24 | United Technologies Corporation | Lightweight blade for gas turbine engine |
| GB201502612D0 (en) * | 2015-02-17 | 2015-04-01 | Rolls Royce Plc | Rotor disc |
| US9803647B2 (en) * | 2015-07-21 | 2017-10-31 | General Electric Company | Method and system for repairing turbomachine dovetail slots |
| US10486785B2 (en) | 2016-10-17 | 2019-11-26 | General Electric Company | Propeller assembly and method of assembling |
| US10689073B2 (en) | 2016-10-17 | 2020-06-23 | General Electric Company | Apparatus and system for marine propeller blade dovetail stress reduction |
| US11052982B2 (en) | 2016-10-17 | 2021-07-06 | General Electric Company | Apparatus for dovetail chord relief for marine propeller |
| US9682756B1 (en) * | 2016-10-17 | 2017-06-20 | General Electric Company | System for composite marine propellers |
| US10633067B2 (en) | 2016-10-17 | 2020-04-28 | General Electric Company | Method and system for improving flow characteristics in marine propellers |
| RU2642976C1 (en) * | 2017-04-13 | 2018-01-29 | Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") | Rotor working wheel of high-pressure compressor of gas turbine engine |
| US11274599B2 (en) | 2019-03-27 | 2022-03-15 | Pratt & Whitney Canada Corp. | Air system switching system to allow aero-engines to operate in standby mode |
| US11391219B2 (en) * | 2019-04-18 | 2022-07-19 | Pratt & Whitney Canada Corp. | Health monitor for air switching system |
| US11274611B2 (en) | 2019-05-31 | 2022-03-15 | Pratt & Whitney Canada Corp. | Control logic for gas turbine engine fuel economy |
| US11859563B2 (en) | 2019-05-31 | 2024-01-02 | Pratt & Whitney Canada Corp. | Air system of multi-engine aircraft |
| US11326525B2 (en) | 2019-10-11 | 2022-05-10 | Pratt & Whitney Canada Corp. | Aircraft bleed air systems and methods |
| US11242761B2 (en) * | 2020-02-18 | 2022-02-08 | Raytheon Technologies Corporation | Tangential rotor blade slot spacer for a gas turbine engine |
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|---|---|---|---|---|
| CN88100958A (en) * | 1987-02-24 | 1988-09-07 | 西屋电气公司 | Steam turbine blade support arrangement |
| US5372481A (en) * | 1993-11-29 | 1994-12-13 | Solar Turbine Incorporated | Ceramic blade attachment system |
| CN1512037A (en) * | 2002-12-11 | 2004-07-14 | ͨ�õ�����˾ | Method and device for assembling turbine engine |
| CN101526013A (en) * | 2008-03-07 | 2009-09-09 | 曼柴油机欧洲股份公司 | Device for fixing turbine blades |
| CN101892866A (en) * | 2009-05-20 | 2010-11-24 | 通用电气公司 | The low stress circumferential dovetail attachment that is used for rotor blade |
Family Cites Families (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| NL4918C (en) * | 1917-05-10 | 1900-01-01 | ||
| NL5896C (en) * | 1918-01-21 | 1900-01-01 | ||
| DE510917C (en) * | 1928-09-11 | 1930-10-24 | Aeg | Method for attaching a blade lock to steam turbines |
| BE441756A (en) * | 1940-06-12 | |||
| GB2097480B (en) | 1981-04-29 | 1984-06-06 | Rolls Royce | Rotor blade fixing in circumferential slot |
| FR2723397B1 (en) | 1994-08-03 | 1996-09-13 | Snecma | TURBOMACHINE COMPRESSOR DISC WITH AN ASYMMETRIC CIRCULAR THROAT |
| US6619924B2 (en) * | 2001-09-13 | 2003-09-16 | General Electric Company | Method and system for replacing a compressor blade |
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| US8500394B2 (en) * | 2008-02-20 | 2013-08-06 | United Technologies Corporation | Single channel inner diameter shroud with lightweight inner core |
| JP5730085B2 (en) * | 2011-03-17 | 2015-06-03 | 三菱日立パワーシステムズ株式会社 | Rotor structure |
-
2012
- 2012-04-30 US US13/459,931 patent/US9068465B2/en active Active
-
2013
- 2013-04-23 EP EP13164867.7A patent/EP2660426B1/en active Active
- 2013-04-26 JP JP2013093292A patent/JP6106021B2/en active Active
- 2013-04-29 RU RU2013119488/06A patent/RU2013119488A/en not_active Application Discontinuation
- 2013-05-02 CN CN201310158615.2A patent/CN103375181B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN88100958A (en) * | 1987-02-24 | 1988-09-07 | 西屋电气公司 | Steam turbine blade support arrangement |
| US5372481A (en) * | 1993-11-29 | 1994-12-13 | Solar Turbine Incorporated | Ceramic blade attachment system |
| CN1512037A (en) * | 2002-12-11 | 2004-07-14 | ͨ�õ�����˾ | Method and device for assembling turbine engine |
| CN101526013A (en) * | 2008-03-07 | 2009-09-09 | 曼柴油机欧洲股份公司 | Device for fixing turbine blades |
| CN101892866A (en) * | 2009-05-20 | 2010-11-24 | 通用电气公司 | The low stress circumferential dovetail attachment that is used for rotor blade |
Also Published As
| Publication number | Publication date |
|---|---|
| EP2660426A3 (en) | 2018-04-25 |
| CN103375181A (en) | 2013-10-30 |
| US9068465B2 (en) | 2015-06-30 |
| EP2660426A2 (en) | 2013-11-06 |
| RU2013119488A (en) | 2014-11-10 |
| JP2013231438A (en) | 2013-11-14 |
| US20130287556A1 (en) | 2013-10-31 |
| JP6106021B2 (en) | 2017-03-29 |
| EP2660426B1 (en) | 2019-06-12 |
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| TR01 | Transfer of patent right |
Effective date of registration: 20231226 Address after: Swiss Baden Patentee after: GENERAL ELECTRIC CO. LTD. Address before: New York State, USA Patentee before: General Electric Co. |